AERODYNAMIC COEFFICIENTS FROM SHOCK EXPANSION THEORY: ANALYTICAL DEVELOPMENT FOR PLANAR SURFACES

Abstract

A simplified version of the shock expansion theory is employed to estimate the unsteady aerodynamic loading on a planar surface. Expressions for oscillatory aerodynamic coef ficients are developed for the case of a three degrees-of-freedom airfoil section.

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Document Details

Document Type
Technical Report
Publication Date
Apr 29, 1963
Accession Number
AD0404922

Entities

People

  • M. H. Lock

Organizations

  • The Aerospace Corporation

Tags

Communities of Interest

  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Air Force
  • Coefficients
  • Control Surfaces
  • Coordinate Systems
  • Equations
  • Flow
  • Free Stream
  • Frequency
  • Geometry
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Shock Waves
  • Steady Flow
  • Two Dimensional
  • Unsteady Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.